[특허]Helicopter

Agusta S.p.A.

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Helicopter

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/04 B64C-021/06 B64D-033/02
미국특허분류(USC)	244/017.11; 244/053B; 244/209
출원번호	US-0481215 (2009-06-09)
등록번호	US-8113461 (2012-02-14)
우선권정보	EP-08425408 (2008-06-10)
발명자 / 주소	Nannoni, Fabio Ballerio, Dante Scandroglio, Alessandro
출원인 / 주소	Agusta S.p.A.
대리인 / 주소	Berenato & White, LLC
인용정보	피인용 횟수 : 2 인용 특허 : 3

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A helicopter comprising a drive having an air intake conduit, a main rotor connected functionally to the drive and a transmission interposed functionally between the main rotor and the drive and housed in a housing. The helicopter further comprises at least one air intake having a first inlet fluidly connected to the intake conduit, at least one second inlet fluidly connected to the housing and deflecting means interacting, in use, with an airflow to divide the airflow into a first and a second airflow. The air intake also has guide means for guiding the...

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1. A helicopter (1) comprising: a fuselage (2);a drive (6) comprising an air intake conduit (12);a main rotor (3) connected functionally to said drive (6);a transmission (9) interposed functionally between said main rotor (3) and said drive (6) and housed in a housing (23); andat least one air intake (20) comprising: a first inlet (21) fluidly connected to said intake conduit (12);at least one second inlet (22) fluidly connected to said housing (23);a first wall (29) defining deflecting means (30) interacting, in use, with an airflow (F) to divide the airflow (F) into a first airflow and a second airflow; andguide means (31, 32, 37, 53) for guiding said first airflow along a first path (P) extending from said deflecting means (30) to said first inlet (21), and for guiding said second airflow along a second path (Q) separate from said first path (P) and extending from said deflecting means (30) to said second inlet (22);said second path (Q) extending between said first wall (29) and said fuselage (2); andsaid first path (P) extending on the opposite side of said first wall (29) to said fuselage (2). 2. The helicopter as claimed in claim 1, wherein said deflecting means (30) are defined by a free first end edge (30) of said first wall (29). 3. The helicopter as claimed in claim 1, wherein said air intake (20) comprises a second wall (35) and a third wall (50) defining said first inlet (21) and said second inlet (22) respectively; said third wall (50) extends between a first surface (31) of said first wall (29) and said fuselage (2), and said second wall (35) projects from a second surface (32), opposite said first surface (31), of said first wall (29); said guide means (31, 32, 37, 53) is defined by said first and second surfaces (31, 32) of said first wall (29), by a portion of said second wall (35) extending between said second surface (32) and said first inlet (21), and by a portion of said third wall (50) extending between said first surface (31) and said second inlet (22). 4. The helicopter as claimed in claim 3, wherein said second wall (35) comprises a first end edge (38) cooperating at least partly with said second surface (32) of said first wall (29) and a second end edge (39) opposite said second end edge (38); said first inlet (21) extending at a distance from said second surface (32) smaller than the distance between said third end edge (39) and said second surface (32). 5. The helicopter as claimed in claim 4, wherein the thickness of said second wall (35), measured perpendicularly to said second surface (32), increases in the direction from said second end edge (38) to said third end edge (39), and decreases in the direction from said third end edge (39) to said first inlet (21). 6. The helicopter as claimed in claim 3, wherein said at least one air intake (20) comprises two second inlets (22); and wherein said third wall (50) comprises a free rounded edge (54) and a third and fourth surfaces (53) converging in said rounded edge (54); said third and fourth surfaces (53) each defining one of said second inlets (22). 7. The helicopter as claimed in claim 6, wherein said rounded edge (54) of said third wall (50) is interposed between said free end edge (30) of said first wall (29) and said second inlets (22). 8. The helicopter as claimed in claim 3, wherein said first, second, and third walls (29, 35, 50) are integral with one another. 9. A helicopter comprising: a drive (6) comprising an air intake conduit (12);a main rotor (3) connected functionally to said drive (6);a transmission (9) interposed functionally between said main rotor (3) and said drive (6) and housed in a housing (23); andat least one air intake (20) comprising: a first inlet (21) fluidly connected to said intake conduit (12);at least one second inlet (22) fluidly connected to said housing (23);a first wall (29) defining deflecting means (30) interacting, in use, with an airflow (F) to divide the airflow (F) into a first airflow and a second airflow; andguide means (31, 32, 37, 53) for guiding said first airflow along a first path (P) extending from said deflecting means (30) to said first inlet (21), and for guiding said second airflow along a second path (Q) separate from said first path (P) and extending from said deflecting means (30) to said second inlet (22);the contour of said first inlet (21) comprising a first tip portion (46), and a second arc-shaped portion (45) located on the opposite side of said first tip portion (46) to a free end edge (30) of said first wall (29);said first tip portion (46) diverging in the direction from said free end edge (30) of said first wall (29) to said second arc-shaped portion (45). 10. A helicopter comprising: a drive (6) comprising an air intake conduit (12);a main rotor (3) connected functionally to said drive (6);a transmission (9) interposed functionally between said main rotor (3) and said drive (6) and housed in a housing (23); andat least one air intake (20) comprising: a first inlet (21) fluidly connected to said intake conduit (12);at least one second inlet (22) fluidly connected to said housing (23);deflecting means (30) interacting, in use, with an airflow (F) to divide the airflow (F) into a first airflow and a second airflow; andguide means (31, 32, 37, 53) for guiding said first airflow along a first path (P) extending from said deflecting means (30) to said first inlet (21), and for guiding said second airflow along a second path (Q) separate from said first path (P) and extending from said deflecting means (30) to said second inlet (22);said drive (6) comprises:a compressor (11) provided to draw a portion (L) of the air flowing through said first inlet (21) and said intake conduit (12);a combustion chamber (13) in use supplied with air compressed by said compressor (11), and causing said compressed air to react with a fuel to produce high-temperature burnt gas;a turbine (14) provided to expand said burnt gas;a nozzle (15) for varying the speed of the burnt gas expanded in said turbine (14); andan exhaust conduit (16) located downstream from said nozzle (15) to expel said burnt gas from said helicopter (1);said helicopter (1) comprising a tap line for drawing off a quota (I) of said first airflow upstream from said compressor (11), and feeding said quota (I) downstream from said turbine (14) to mix said quota (I) with said burnt gas from said turbine (14).

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Helicopter

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이 특허에 인용된 특허 (3)

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